Aircraft Safety Livesaving System

Abstract

An aircraft safety lifesaving system, disclosing an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body. A safety cabin is provided at the top of the aircraft body, and a deceleration device in the safety cabin is ejected in an emergency to assist the aircraft body to decelerate; the damping and buffering mechanism extends below the wheel body, and the damping and buffering mechanism contacts with the ground first.

What is claimed is: 
     
         1 . An aircraft safety lifesaving system, comprising an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land;
 a damping and buffering mechanism is provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body to buffer the impact force when the aircraft body descends.   
     
     
         2 . The aircraft safety lifesaving system according to  claim 1 , wherein the damping and buffering mechanism comprises a friction plate, a vertical strut and an elastic component, wherein:
 the vertical strut is a hydraulic support provided vertically, the top end of the vertical strut is connected with the bottom of the aircraft body, and the elastic component is positioned between the vertical strut and the friction plate and connects the vertical strut and the friction plate;   the friction plate is capable of moving to the position below the wheel body when the vertical strut extends out so as to have friction with the ground for deceleration, and the elastic component is capable of elastically deforming when the friction plate contacts with the ground so as to buffer an external force.   
     
     
         3 . The aircraft safety lifesaving system according to  claim 2 , wherein the friction plate extends along the length direction of the aircraft body, and more than two vertical struts are connected to both sides of the upper surface of the friction plate, and all the vertical struts are arranged at intervals along the extending direction of the friction plate. 
     
     
         4 . The aircraft safety lifesaving system according to  claim 2 , wherein the damping and buffering mechanism further comprises an inclined strut, the inclined strut is a hydraulic support, the inclined strut is arranged obliquely, and the inclined strut has a fixed end connected with the bottom of the aircraft body and a telescopic end connected with the side of the vertical strut. 
     
     
         5 . The aircraft safety lifesaving system according to  claim 1 , wherein an interlayer is formed in the housing of the aircraft body, the interlayer is communicated with the safety cabin, a reinforcing band is accommodated in the interlayer, and the reinforcing band is fixed around the aircraft body for a circle and extends into the safety cabin;
 a plurality of safety cabins are arranged at intervals along the length direction of the aircraft body, and all the deceleration devices in the safety cabin are fixedly connected with the reinforcing bands.   
     
     
         6 . The aircraft safety lifesaving system according to  claim 1 , wherein the deceleration device comprises a brake parachute located on the fuselage and a brake parachute located at the tail of the aircraft body, wherein:
 the brake parachute on the fuselage comprises one or more layers, and when the brake parachute has more than two layers, the bottom of the brake parachute on the upper layer is fixedly connected with the top of the brake parachute on the lower layer.   
     
     
         7 . The aircraft safety lifesaving system according to  claim 1 , wherein the deceleration device comprises a propeller on the fuselage, the propeller is connected with a generator, the generator is electrically connected with a storage battery, and the storage battery is electrically connected with an electrical device in the aircraft body. 
     
     
         8 . The aircraft safety lifesaving system according to  claim 1 , wherein deceleration wings are also provided on both sides of the aircraft body, the deceleration wings have an arc structure protruding toward the nose, there are more than two deceleration wings on each side, and all the deceleration wings located on the same side of the aircraft body are arranged at intervals in the length direction of the aircraft body. 
     
     
         9 . The aircraft safety lifesaving system according to  claim 8 , wherein the deceleration wing is rotatably connected with the aircraft body, and a hydraulic rod assembly is provided between the side of the deceleration wing away from the nose and the aircraft body;
 the hydraulic rod assembly comprises one or more hydraulic rod bodies, the fixed ends of the hydraulic rod bodies are fixedly connected with the aircraft body, and the telescopic ends of the hydraulic rod bodies are fixedly connected with the deceleration wing;   the deceleration wing has an unfolded state and a folded state, and the hydraulic rod is capable of pushing the deceleration wing to rotate in the direction away from the aircraft body when extending out, so that the deceleration wing is in the unfolded state; the hydraulic rod is capable of pulling the deceleration wing to rotate in the direction close to the aircraft body when contracting, so that the deceleration wing is in the folded state.   
     
     
         10 . The aircraft safety lifesaving system according to  claim 9 , wherein an escape exit is provided at the position corresponding to each deceleration wing on the aircraft body, and the escape exit is capable of being covered by the deceleration wing in the folded state;
 the escape exit is provided with a push-pull door body; and an extendable escape ladder is provided at the escape exit.